P
US9284231B2ActiveUtilityPatentIndex 67

Hydrocarbon film protected refractory carbide components and use

Assignee: MINNEAR WILLIAM PAULPriority: Dec 16, 2011Filed: Dec 16, 2011Granted: Mar 15, 2016
Est. expiryDec 16, 2031(~5.5 yrs left)· nominal 20-yr term from priority
Inventors:MINNEAR WILLIAM PAULBUNKER RONALD SCOTTJOSHI NARENDRA DIGAMBEREVULET ANDREI TRISTAN
C04B 41/009F02C 7/12F01D 15/10C04B 41/80F05D 2260/232F01D 25/12C04B 41/0072F02C 7/16Y02T50/672Y02T50/676C04B 35/56C04B 35/565C04B 35/806C04B 41/4529Y02T50/60
67
PatentIndex Score
3
Cited by
27
References
10
Claims

Abstract

A turbine power generation system with enhanced stabilization of refractory carbides provided by hydrocarbon from high carbon activity gases is disclosed. The disclosure also includes a method of using high carbon activity gases to stabilize hot gas path components.

Claims

exact text as granted — not AI-modified
What is claimed: 
     
       1. A method for stabilizing a refractory carbide hot gas path component comprising:
 combusting a fuel in a combustor to form a gas stream comprising post-combustion gases; and 
 delivering a high carbon activity gas to at least a portion of a hot gas path component thermally coupled to a hot gas path, wherein the component comprises a plurality of film holes disposed to cover at least a portion of the component with a layer of gas, and wherein delivering the high carbon activity gas comprises introducing the high carbon activity gas via the plurality of film holes; 
 wherein at least a portion of the hot gas path component comprises refractory carbide. 
 
     
     
       2. The method of  claim 1 , further comprising selectively controlling a flow of the high carbon activity gas to the hot gas path. 
     
     
       3. The method of  claim 1 , wherein the hot gas path component is selected from a combustor component, a vane, a blade, a rocket component, a ram jet component, a scram jet component, and a shroud. 
     
     
       4. The method of  claim 1 , wherein the hot gas path component comprises a portion of a turbine system. 
     
     
       5. The method of  claim 4 , wherein the turbine system comprises:
 the combustor configured to combust air with the fuel to produce an exhaust gas stream; 
 a turbine configured to convert energy of the exhaust stream into useful mechanical energy; and 
 a first conduit configured to deliver the high carbon activity gas to the hot gas path. 
 
     
     
       6. The method of  claim 5 , wherein the turbine system further includes at least one of:
 a compressor configured to compress air; 
 a valve configured to selectively control an amount of the high carbon activity gas distributed to the hot gas path; 
 a generator configured to convert mechanical energy produced by the turbine into electrical energy; and 
 a shaft linking the compressor, the turbine, and the generator to allow mechanical energy produced by the turbine to be utilized by the generator and the compressor. 
 
     
     
       7. The method of  claim 1 , wherein the high carbon activity gas comprises at least one hydrocarbon fuel. 
     
     
       8. The method of  claim 7 , wherein the high carbon activity gas further comprises carbon dioxide. 
     
     
       9. The method of  claim 8 , further comprising sequestering carbon dioxide from the post-combustion gases in a reservoir; and wherein delivering comprises adding the sequestered carbon dioxide in the high carbon activity gas. 
     
     
       10. The method of  claim 1 , wherein said refractory carbide comprises a ceramic matrix composite.

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